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LWK 79-100 (lwk79100-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LWK 79-100 (lwk79100-il)
Reynolds number: 50,000
Max Cl/Cd: 25.9 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk79100-il-50000.txt
Download as CSV file: xf-lwk79100-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 79-100                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.7269   0.09239   0.08554   0.0032   1.0000   0.1681
  -9.250  -0.7081   0.08803   0.08113   0.0047   1.0000   0.1647
  -9.000  -0.8013   0.07137   0.06439  -0.0110   1.0000   0.1389
  -8.750  -0.8086   0.06569   0.05854  -0.0123   1.0000   0.1382
  -8.500  -0.8135   0.06016   0.05273  -0.0132   1.0000   0.1376
  -8.250  -0.8157   0.05481   0.04696  -0.0136   1.0000   0.1377
  -8.000  -0.8120   0.04983   0.04144  -0.0136   1.0000   0.1381
  -7.750  -0.8029   0.04534   0.03630  -0.0131   1.0000   0.1393
  -7.500  -0.7824   0.04250   0.03354  -0.0125   1.0000   0.1465
  -7.250  -0.7675   0.03910   0.02947  -0.0118   1.0000   0.1528
  -7.000  -0.7456   0.03614   0.02641  -0.0111   1.0000   0.1597
  -6.750  -0.7247   0.03361   0.02356  -0.0103   1.0000   0.1713
  -6.500  -0.7019   0.03133   0.02108  -0.0095   1.0000   0.1853
  -6.250  -0.6782   0.02924   0.01900  -0.0087   1.0000   0.2034
  -6.000  -0.6554   0.02732   0.01710  -0.0076   1.0000   0.2298
  -5.750  -0.6333   0.02554   0.01553  -0.0064   1.0000   0.2659
  -5.500  -0.6129   0.02401   0.01431  -0.0048   1.0000   0.3158
  -5.250  -0.5936   0.02292   0.01366  -0.0026   1.0000   0.3771
  -5.000  -0.5746   0.02244   0.01361   0.0003   1.0000   0.4431
  -4.750  -0.5552   0.02259   0.01404   0.0038   1.0000   0.5036
  -4.500  -0.5354   0.02297   0.01458   0.0075   1.0000   0.5546
  -4.250  -0.5159   0.02322   0.01486   0.0114   1.0000   0.5994
  -4.000  -0.4973   0.02318   0.01481   0.0149   1.0000   0.6409
  -3.750  -0.4782   0.02312   0.01477   0.0188   1.0000   0.6755
  -3.500  -0.4596   0.02285   0.01449   0.0224   1.0000   0.7090
  -3.250  -0.4410   0.02248   0.01406   0.0258   1.0000   0.7410
  -3.000  -0.4213   0.02207   0.01362   0.0288   1.0000   0.7712
  -2.750  -0.3989   0.02167   0.01318   0.0313   1.0000   0.8002
  -2.500  -0.3715   0.02132   0.01278   0.0328   1.0000   0.8286
  -2.250  -0.3354   0.02105   0.01239   0.0325   1.0000   0.8566
  -2.000  -0.2882   0.02086   0.01207   0.0298   1.0000   0.8841
  -1.750  -0.2304   0.02066   0.01170   0.0246   1.0000   0.9108
  -1.500  -0.1496   0.02037   0.01121   0.0146   1.0000   0.9346
  -1.250  -0.0876   0.01983   0.01057   0.0072   1.0000   0.9571
  -1.000  -0.0237   0.01913   0.00983  -0.0011   1.0000   0.9777
  -0.750   0.0386   0.01836   0.00905  -0.0096   1.0000   0.9977
  -0.500   0.0522   0.01804   0.00884  -0.0099   1.0000   1.0000
  -0.250   0.0407   0.01805   0.00896  -0.0068   1.0000   1.0000
   0.000   0.0000   0.01822   0.00916   0.0000   1.0000   1.0000
   0.250  -0.0407   0.01805   0.00896   0.0068   1.0000   1.0000
   0.500  -0.0521   0.01804   0.00883   0.0099   1.0000   1.0000
   0.750  -0.0387   0.01836   0.00905   0.0097   0.9978   1.0000
   1.000   0.0237   0.01913   0.00982   0.0011   0.9778   1.0000
   1.250   0.0874   0.01982   0.01056  -0.0071   0.9571   1.0000
   1.500   0.1495   0.02037   0.01120  -0.0146   0.9347   1.0000
   1.750   0.2305   0.02066   0.01170  -0.0246   0.9108   1.0000
   2.000   0.2883   0.02085   0.01206  -0.0298   0.8840   1.0000
   2.250   0.3354   0.02105   0.01239  -0.0325   0.8566   1.0000
   2.500   0.3715   0.02132   0.01277  -0.0328   0.8286   1.0000
   2.750   0.3989   0.02167   0.01318  -0.0313   0.8003   1.0000
   3.000   0.4213   0.02207   0.01362  -0.0288   0.7712   1.0000
   3.250   0.4410   0.02248   0.01406  -0.0258   0.7409   1.0000
   3.500   0.4596   0.02285   0.01449  -0.0224   0.7090   1.0000
   3.750   0.4781   0.02312   0.01477  -0.0188   0.6755   1.0000
   4.000   0.4973   0.02318   0.01481  -0.0149   0.6409   1.0000
   4.250   0.5159   0.02322   0.01486  -0.0113   0.5994   1.0000
   4.500   0.5354   0.02297   0.01458  -0.0075   0.5545   1.0000
   4.750   0.5552   0.02259   0.01404  -0.0037   0.5036   1.0000
   5.000   0.5746   0.02244   0.01361  -0.0003   0.4431   1.0000
   5.250   0.5936   0.02292   0.01366   0.0026   0.3771   1.0000
   5.500   0.6129   0.02400   0.01431   0.0048   0.3158   1.0000
   5.750   0.6333   0.02554   0.01553   0.0064   0.2659   1.0000
   6.000   0.6555   0.02732   0.01710   0.0076   0.2297   1.0000
   6.250   0.6782   0.02925   0.01900   0.0087   0.2033   1.0000
   6.500   0.7020   0.03133   0.02109   0.0095   0.1853   1.0000
   6.750   0.7248   0.03360   0.02355   0.0103   0.1711   1.0000
   7.000   0.7457   0.03614   0.02641   0.0111   0.1596   1.0000
   7.250   0.7676   0.03911   0.02948   0.0118   0.1528   1.0000
   7.500   0.7825   0.04250   0.03354   0.0125   0.1464   1.0000
   7.750   0.8030   0.04536   0.03632   0.0131   0.1392   1.0000
   8.000   0.8121   0.04985   0.04145   0.0136   0.1381   1.0000
   8.250   0.8158   0.05484   0.04698   0.0136   0.1377   1.0000
   8.500   0.8139   0.06018   0.05275   0.0131   0.1376   1.0000
   8.750   0.8077   0.06577   0.05863   0.0121   0.1380   1.0000
   9.000   0.8011   0.07140   0.06442   0.0109   0.1388   1.0000
   9.250   0.6017   0.10850   0.10124  -0.0331   0.3378   1.0000
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